The GSLV-III or Geosynchronous Satellite Launch Vehicle Mark III is a launch vehicle developed by the Indian Space Research Organisation. It is intended to launch satellites into geostationary orbit and as a launcher for an Indian crew vehicle. The GSLV MK-3 will feature an Indian cryogenic third stage and a higher payload capacity than the current GSLV.
Development for the GSLV Mk III began in the early 2000s, with the first launch planned for 2009-2010. Several factors have delayed the program, including the 15 April 2010 failure of the ISRO-developed cryogenic upper stage on the GSLV Mk II.
A suborbital flight test of the GSLV Mk3 launcher, with a passive cryogenic third stage, was successfully carried out on 18 December 2014, and was used to test a crew module on a suborbital trajectory. The first orbital flight is planned to take place in 2016. The first flight with a crew on board would take place after 2020.
Function Medium lift launch vehicle
Manufacturer Indian Space Research Organisation
Country of origin India
Size
Height 43.43 m (142.5 ft)
Diameter 4.0 m (13.1 ft)
Mass 630,580 kg (1,390,190 lb)
Stages 3
Capacity
Payload to
LEO 10,000 kg (22,000 lb)
Payload to
GTO 4,000 kg (8,800 lb)-5,000 kg (11,000 lb)[2]
Launch history
Status Launch Rehearsal
Launch sites Satish Dhawan Space Centre SLP, Andhra Pradesh, India
Total launches 1 (2 stage version)
Successes 1 (2 stage version)
First flight 18 December 2014 (2 stage version; sub-orbital flight)
2016 (full version)
Booster Stage – S-200
Length 25.75 m (84.5 ft)
Diameter 3.2 m (10 ft)
Empty mass 31,000 kg (68,000 lb)
Gross mass 238,000 kg (525,000 lb)
Engines 2 Solid
Thrust 5,150 kN (525 tf) each
Specific impulse 227 (sea level)
274.5 (vacuum)
Burn time 130 sec
Fuel Solid
Core Stage – L-110
Length 17 m (56 ft)
Diameter 4 m (13 ft)
Engines 2 Vikas
Thrust 1,400 kN (140 tf)
Specific impulse 281 sec
Burn time 200 sec
Fuel UH 25/N2O4
Upper Stage – C-25
Engines 1 CE-20
Thrust 200 kN (20 tf)
Specific impulse 450 sec
Burn time 580 sec
Fuel LOX/LH2
